WO2009032221A1 - Procédé pour inspecter et remettre en état des composants mécaniques - Google Patents

Procédé pour inspecter et remettre en état des composants mécaniques Download PDF

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Publication number
WO2009032221A1
WO2009032221A1 PCT/US2008/010286 US2008010286W WO2009032221A1 WO 2009032221 A1 WO2009032221 A1 WO 2009032221A1 US 2008010286 W US2008010286 W US 2008010286W WO 2009032221 A1 WO2009032221 A1 WO 2009032221A1
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WO
WIPO (PCT)
Prior art keywords
component
damage
extent
engineering
components
Prior art date
Application number
PCT/US2008/010286
Other languages
English (en)
Inventor
Mark D. Michaud
Gary Sroka
Lane W. Winkelmann
Original Assignee
Rem Technologies Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rem Technologies Inc filed Critical Rem Technologies Inc
Priority to JP2010522972A priority Critical patent/JP5714330B2/ja
Priority to CA2695630A priority patent/CA2695630A1/fr
Priority to DK08795724.7T priority patent/DK2195139T3/en
Priority to US12/675,712 priority patent/US9180568B2/en
Priority to CN200880104960.5A priority patent/CN101801602B/zh
Priority to EP08795724.7A priority patent/EP2195139B1/fr
Priority to ES08795724.7T priority patent/ES2530193T3/es
Publication of WO2009032221A1 publication Critical patent/WO2009032221A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B5/00—Machines or devices designed for grinding surfaces of revolution on work, including those which also grind adjacent plane surfaces; Accessories therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B31/00—Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work and/or the abrasive material is loose; Accessories therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12993—Surface feature [e.g., rough, mirror]

Definitions

  • the invention relates generally to methods of refurbishing or restoring metal components back to an acceptable operational condition using subtractive surface engineering techniques that maintain the component within geometrical tolerance.
  • the method is particularly applicable to components manufactured or finished to tight tolerances that are used in metal to metal contact mechanisms and where the original manufacturing geometric specification may be absent or unavailable.
  • the method further relates to a method of assessment of such components for refurbishment and the refurbished products thereof.
  • ESD Engineering Specification Drawing
  • the ESD will contain information such as all dimensions used to originally manufacturer the component, the tolerances on all dimensions, the component's material and heat treatment, and the like. This information is needed to allow the machinist to correctly regrind or re-machine the component's critical surfaces and to inspect the results.
  • CST Component Specific Tooling
  • DM_US:21430364_l suitable tooling to fixture and/or inspect the component.
  • regrinding may remove so much material that the component becomes undersized. This cannot always be determined prior to commencing work and the high levels of scrap in such processes considerably increase the overall cost of the work.
  • a regrinding operation will comprise setting up and aligning the component in the grinder or lathe, performing a first pass, inspecting and adjusting the alignment of the component and performing a further pass to remove the desired quantity of material.
  • a number of passes may be required merely to achieve correct alignment.
  • the minimum amount of material that can be effectively ground in a single pass is 10-20 microns. If three passes are required to complete the component, as much as 60 microns may have been removed. For e.g. a gear tooth in which material has been removed from both faces of the tooth, a total dimensional change of 120 microns may result.
  • DM_US:21430364_l be put back into service without having been successfully restored.
  • a method for inspecting and/or refurbishing a used or otherwise damaged component using a Subtractive Surface Engineering (SSE) process to remove material from worn or damaged critical surfaces of the component, the method comprising: initially performing the process on the component to remove a first quantity of material from the surfaces; inspecting the surface of the component to determine the extent of damage; and subsequently further performing the process to remove a further quantity of material.
  • SSE Subtractive Surface Engineering
  • the number of candidates for receiving the full refurbishment process may be increased and the number of refurbished components subsequently scrapped due to incorrect damage determination is reduced.
  • the additional work of performing the initial process to remove the first quantity of material may be offset by the reduction in scrapped components.
  • the possibility of incorrectly returning a component to service due to surface distress after the regrinding or remachining method due to masking the underlying damage during inspection is eliminated when using this SSE process.
  • inspection may take place by any conventional method, suitable for determining the extent of the apparent damage.
  • extent of the apparent damage is understood to cover any suitable measure of damage, including but not limited to depth, area, roughness etc.
  • DM_US:21430364_l depth is understood to be the deepest point normal to the surface; "area” is understood to refer to the area of the damage in the plane of the surface; “apparent” is intended to refer to the fact that the damage is visible from the exterior either to the naked eye or with magnification, with or without marker or fluorescent penetrant. Reference to the fact that damage determination is carried out after initially performing the process is intended to refer to the fact that no initial preselection (e.g. scrapping) of components based on surface conditions is carried out prior to performing the SSE process. It will be understood that selection and scrapping of components due to visible macro-scale damage such as broken teeth or bearings may take place at an early stage prior to processing.
  • a preferred method of inspection is carried out by visually identifying and marking damage such as FOD, wear or micropitting in a well lit area, photographically recording the locations using a measuring instrument such as a ruler, taking direct profilometer measurements across the damage and documenting the extent of damage.
  • another preferred method of inspection is the graphite and tape lifting method described by McNiff, B; Musial, W.; Errichello, R.; "Documenting the Progression of Gear Micropitting in the NREL Dynamometer Test Facility"; 2002 Conference Proceedings of the American Wind Energy Association WindPower 2002 Conference, 3-5 June 2002, Portland, Oregon, Washington, DC: American Wind Energy Association, 2002; 5pp., the contents of which are hereby incorporated by reference in their entirety.
  • This graphite and tape lifting method is particularly useful for mapping the locations of the damage for comparison during the repairing phases of the component refurbishment.
  • references to SSE processes are intended to refer to planarizing processes capable of simultaneously removing material from the treated surfaces of a metal component in small, substantially uniform, controlled amounts without causing surface distortion.
  • the SSE processes can be carried out singlely or on large quantities of components at one time.
  • Processes falling within the definition of SSE processes include but are not limited to vibratory finishing and chemically accelerated vibratory finishing using non-abrasive media processes, abrasive media processes, drag finishing, spindle deburr machines, centrifugal disc machines, abrasive media tumbling, loose abrasive tumbling, spindle deburr machines, centrifugal disc machines, AbralTM processes and paste based processes.
  • Preferred processes are isotropic in nature and cause substantially no directionally oriented residual traces on the finished
  • an SSE process By using an SSE process, minimal amounts of material can be removed from at least the worn or damaged critical surfaces safely and cost effectively. Refurbishment of high value used metal components can thus be achieved.
  • an SSE process removes material without surface distortion and therefore exposes a true picture for inspection of the resulting surface's properties.
  • the true extent of micropitting, pitting, scuffing, corrosion or dynamic fatigue cracking can better be determined.
  • the presence and/or extent of subsurface damage such as subsurface microcracks may only become aparent and/or measureable after removal of the outer layer via the SSE process.
  • the proposed SSE processes are also believed to be more fail-safe than previously used regrinding or re-machining processes. In particular, they are less susceptible to set-up failure due to incorrect location of a component in the treatment machine. Furthermore, grinding and machining processes can be prone to metallurgical damage known as temper burn. These machining processes usually require a final Nital etch inspection to ensure that temper burn did not ruin the component. The present invention does not require temper burn inspection although it is understood that this may be carried out for other reasons.
  • the method may comprise : performing SSE for a short time to uncover surface damage; inspecting the surface; determining the extent of surface damage and initially predicting stock removal - if stock removal prediction exceeds geometrical tolerance, component is scrap - if stock removal prediction is within acceptable geometrical tolerance then proceed; performing SSE to uncover sub-surface damage; monitoring component surface to determine extent or presence of sub-surface damage and modify initial stock removal estimate if needed - if stock removal prediction exceeds geometrical tolerance, component is scrap - if stock removal prediction is within acceptable geometrical tolerance, then proceed; continuing SSE to remove the predicted stock removal; finally inspecting the treated surfaces to determine if component is suitable for re-use. In this manner,
  • DM_US:2I43O364 1 the progress of the sub-surface damage can be observed as material is removed and a determination can be made as to if and when a component has been satisfactorily refurbished.
  • an important indicator for the SSE process is not always the overall depth of the damage but the point of maximum surface area of the damage or a point of maximum surface roughness. Initial removal of the surface material may cause the apparent damage to grow in extent. Such masked damage becomes exposed on removal of material. Once it has reached its maximum extent and begins to decrease in area and/or depth and/or roughness, the process may be terminated, even though damage such as residual micropitting or corrosion pitting remains.
  • the component may be successfully treated even though the full depth of the damage is greater than could have acceptably been removed without causing the component to become out of tolerance.
  • micropitting itself is not necessarily detrimental and can remain stable during prolonged use. Removal of the undercut, masked and unstable metal is believed to leave a generally stablised residual micropit area that will not grow or produce further debris when returned to service. Further information regarding the nature of micropitting and other surface and sub-surface damage is provided by the above incorporated reference by R. L. Errichello [0021]
  • components having damage comprising e.g.
  • micropitting the method may include determining an extent and location of at least certain micropit areas whereby during subsequent stages, the depth, roughness and/or surface area of the micropit areas is monitored and the process is terminated once this has indicated a trend in reduction. This can be determined by noting a point at which a subsequent measurment reveals the extent of damage to be equal to or preferably less than a previously determined extent of damage. According to an important advantage of SSE processes, since the component does not need to be "set-up" or accurately located, it may easily be removed for inspection, if required. Furthermore, since the SSE process is effectively a continuous process, inspection can be repeated as frequently as desired, allowing extremely accurate monitoring of the progress of damage removal.
  • the SSE process can be carried out while ensuring that the component stays within geometrical tolerance based only on general knowledge of the
  • DM_US:21430364_l component such as its quality grade.
  • the process may be terminated on the basis of an amount of damage remaining or when the damage has been substantially removed.
  • the point at which the damage is substantially removed can be precisely determined.
  • substantially removed may be defined on a case-by-case basis according to the desired finish required. It may be chosen as the point, where for e.g. the deepest damage being treated: damage has disappeared entirely; damage depth is less than 5% of its original depth; damage depth is less than 10 micron; damage area is less than 50%, 30% or 10% of its original extent; surface roughness is decreasing; Ra is less than 0.25 micron.
  • a thickness of between 0.1 micron and 10 microns of material is removed during the initial SSE process stages. This quantity of material has been found appropriate for revealing the initial extent of actual damage in most cases. It is understood that greater or lesser quanties of material may be removed in subsequent stages in order to further reveal, monitor and remove damage. Calculation of subsequent quantities of material for removal may be based on the inspection after initial processing. [0024] An important aspect of the invention is the monitoring of the amount of material removed. For many SSE processes, a witness coupon of the same or similar material as the component under refurbishment may be used. This is subjected to the same conditions as the component and its reduction in size may be monitored using a micrometer. Such a procedure is however sensitive to certain factors.
  • the witness coupon must be of the same or similar metallurgical composition to the component in order to be consumed at the same rate. Furthermore, because of its distinct geometry, its reduction in size will not be identical to that of the component.
  • material removal may be based on the processing time. In the case of the preferred process of chemically accelerated vibratory finishing, the operator may know that certain steel grades are consumed at the rate of 1 micron per hour and adjust the process accordingly. Such a process is also subject to error, since, for an unknown component, an estimation of e.g. the steel grade is required and other factors such as corrosion or surface finish may affect the result.
  • the procedure may be monitored by means of depth indicators provided on the surface of the
  • DM_US:21430364_l component to be processed may be grooves, notches, patterns or the like of known depth or geometry whereby removal of a given quantity of material causes the indicator to change or disappear.
  • Such indicators may be provided at one or more locations on the relevant surfaces and may be provided to indicate one depth or a series of depths.
  • the depth indicators may also be in the form of known markings already present on the component e.g. in the case of engineered components, the removal of residual grind lines may be used.
  • grind lines may vary between components, their use has surprisingly been found convenient since their depth is generally related to the quality and tolerances of the component being refurbished: a high tolerance component may have very fine residual grind lines of 1 micron depth while a lower tolerance component might have grind lines of 10 micron depth. Removal of the grind lines (or other indicators) can easily be ascertained in situ by visual inspection using e.g. 10x magnification. The indicator may also be used to callibrate the process for further material removal. Thus, if 2 microns is removed in 1 hour of processing using chemically accelerated vibratory finishing, an eight hour process could be expected to remove 16 microns.
  • the method may be carried out on a plurality of used components, whereby after initially performing the process, on inspection, those components are discarded where the extent of damage is greater than a predetermined permissible amount (e.g. where dynamic fatigue cracks are revealed).
  • a predetermined permissible amount e.g. where dynamic fatigue cracks are revealed.
  • thousands of components can be refurbished at one time in a particularly cost effective manner.
  • increased efficiency may be achieved and an overall increased recovery rate (i.e. reduced wastage).
  • the plurality of used components may be simultaneously refurbished whereby at least during the SSE process, the components are all subjected to the same process conditions.
  • all components may be subjected to SSE processing without initial inspection for a predetermined period of time based on a statistically calculated maximum material quantity to be removed. Thereafter, the parts may be inspected, either individually or on a sample basis and a determination may be made as to whether the parts are accepted or scrapped. In this particular case, no subsequent further processing would be carried out since material removal is initially calculated to achieve the maximum statistically acceptable removal while remaining in geometric
  • the components may be identical or different. Simultaneous processing may thus be carried out on a large number of identical components or a number of different components e.g. all the gears, shafts, bearings etc from a single machine. Because individual set-up is not required, the components may, at least initially, be easily treated together and thus subject to the same process conditions. This may be beneficial e.g. from a quality control perspective since testing of one component for surface finish could be expected to apply equally to another component. This may be applicable in particular where all components are metallurgically similar but may also be applied in cases of dissimilar materials. In certain circumstances, parts of components that are not intended for treatment may be masked or may be masked after partial completion of the procedure.
  • the SSE process can be carried out via mass finishing equipment such as vibratory bowls and tubs, spindle and drag finishing machines and the like, using abrasive media processes, abrasive compound processes or chemically accelerated vibratory machining processes with abrasive or non-abrasive media.
  • a most preferred procedure is a chemically accelerated vibratory superfinishing process. This process has shown itself to be extremely effective in producing an isotropic finish of extremely low surface roughness (Ra of less than 0.1 micron). Furthermore it has the added advantage that residual corrosion pits may be stabilized since the mild phosphate active chemistry has the ability to convert the ferric oxide to ferric phosphate, thus inhibiting further propagation.
  • the SSE process is capable of achieving a surface finish Ra of less than 0.25 microns.
  • Ra surface finish
  • the component refurbished it also benefits from the known advantages of superfinished ultra-smooth surfaces. This may be achieved in a single procedure at a single facility.
  • the method may be performed without reference to the component's engineering specification drawing or an equivalent specification sheet.
  • the persons performing the method are thus less bound by limitations that may be imposed by the manufacturer - in particular in circumstances where the ESD may not even be made available to third parties.
  • the same SSE processes and equipment can thus also be used to refurbish geometrically different components economically whether a few in number or many thousands.
  • the procedure needs much less manpower, time and expense for set up and processing than the
  • the invention further relates to an engineering component refurbished according to the method described above.
  • the refurbished component may have an amount of material removed, sufficient to stabilise damage due to e.g. foreign object damage, scoring, micropitting, pitting, spalling, corrosion and the like.
  • the component may in particular be distinguished by the presence of residual stabilized damage.
  • the component has surfaces finished to a surface roughness Ra of less than 0.25 microns although finishes of less than 0.1 microns or even less than 0.05 microns may also be achieved.
  • the edges or borders of the pits may be planarized by the process without inducing further distress to the region.
  • the component according to the invention may be any metal engineering component selected from the group consisting of: gears, shafts, bearings, pistons, axles, cams, seats, seals.
  • the invention is also considered to include sets of components e.g. for a single machine, in which each component has been finished by the same process to the same final condition.
  • the invention in another aspect, relates to a method of inspecting used engineering components for sub-surface damage, using a subtractive surface engineering process to remove material from critical surfaces of the component, the method comprising: performing the process on the components to remove a quantity of material from the surfaces; inspecting the surfaces of the components to determine an extent of apparent damage; and on the basis of the inspection, determining whether the component is suitable for re-use or whether the component should be scrapped.
  • all components may be processed an amount sufficient to maintain the component within the tolerance required. Determination may then be made on the basis of e.g. an absolute maximum size or depth of residual damage.
  • the method may comprise additionally performing at least
  • DM_US:21430364_! one further inspection cycle of material removal and inspection before the determination is made.
  • the inspection cycle may be repeated until the extent of the apparent damage has stabilised. For e.g. micropitting, this may comprise determining a size, depth and/or roughness of at least one micropit region and comparing this with an extent determined in a previous cycle.
  • the process may e.g. be terminated when the extent of micropitting is less than that determined in a previous cycle. Alternatively, the process may be terminated at the point at which the damage has been substantially removed.
  • Other features of the method of inspection may be substantially as described above in the context of refurbishment.
  • FIGS. IA - D show graphite lift records of a tooth of a wind turbine gear at various stages during its refurbishment according to an embodiment of the invention.
  • FIGS 2A - D show prof ⁇ lometer traces across a region of micropitting of the tooth recorded in Figs IA - D; and
  • FIGS 3A, B show profilometer traces across a region of micropitting for a tooth according to a second exemplary embodiment of the invention.
  • surface damage such as FOD, corrosion, micropitting and macropitting were documented with photography, graphite lift and profilometry, using the prof ⁇ lometer according to Table ⁇ .
  • Figure IA shows a graphite lift of what is suspected to be micropitting on the flank of a tooth subsequently identified as tooth 1.
  • An arrow indicates the area of damage for prof ⁇ lometer measurement. This area was chosen as an exemplary measurement location due to the severity of the damage and the uniqueness of the damage spot making it easy to find throughout the testing.
  • Figure 2A is the prof ⁇ lometer surface roughness trace across the area of micropitting identified on tooth 1, indicating Ra -18 microinches (.457 microns), Rmax -158 microinches (4.0 microns) and Rz -90 microinches (2.29 microns). The vertical scale of the trace is 100 microinches (0.25 microns). The results are shown in Table VII below.
  • the machine was started along with the flow of refinement chemistry.
  • the gear was totally submerged under the media and completely wetted with refinement chemistry.
  • the vibratory bowl had a continuous flow of refinement chemistry into it at all times.
  • the vibratory bowl was not fitted with a drain valve such that the refinement chemistry continually drained from three separate slotted drain locations.
  • the gear was processed for one hour of refinement and then removed from the bowl for inspection.
  • the vibratory bowl and refinement chemistry flow were stopped during the inspection. Tooth one was located, cleaned with a damp cloth and dried.
  • This increase in surface roughness (Ra, Rmax and Rz) is an indication that there was "surface distortion" which masked the true depth of the damage seen on the surface.
  • DMJJS 21430364 1 inspection The vibratory bowl and refinement chemistry flow were stopped during the inspection. Tooth 1 was located, cleaned with a damp cloth and dried. The reduction in micropitting area on tooth 1 was documented with a graphite lift as shown in Fig 1C, which shows a reduction in micropitting area. It can also be seen that the residual grinding lines imparted during the gears original manufacturing have been substantially removed.
  • Fig. 2C is the surface roughness trace across the area of micropitting identified on tooth 1 during the initial inspection. It indicates values for Ra - 11 microinches (.279 microns); Rmax - 282 microinches (7.16 microns); and Rz - 71 microinches
  • Fig. 2D is the surface roughness trace across the area of micropitting identified on tooth 1 during the initial inspection. It indicates values for Ra - 3 microinches (.076 microns); Rmax - 23 microinches (.58 microns); and Rz - 17 microinches (.43 microns). It is noted that the surface roughness has decreased during the extended process to a value significantly below the initial values.
  • the gear was deemed refurbished after the 4 hr inspection on the basis of a steadily decreasing roughness and area of residual surface damage and a value of Ra below 12 microinches (0.3 microns).
  • the residual surface damage remaining was small in individual area and widely spaced such that a significant stabilized surface area remained in-between the residual damage.
  • all grind lines imparted during the original manufacturing were removed from the tooth flanks. No new damage was observed upon completion of the process however, the residual damage is evident through visual and graphite lift inspection.
  • DM US 21430364_l [0057] The gear was unpacked from shipping material and visually inspected for macro-scale damage. Surface damage such as FOD and micropitting were documented with photography, prof ⁇ lometry and graphite lift techniques.
  • Fig. 3A is the surface roughness trace across an area of micropitting using the profilometer according to Table EX with a vertical scale of 10 microns.
  • the machine was started along with the flow of refinement chemistry as indicated in Table IV above but at a slightly higher flow rate of 32 litres/hour.
  • the gear was totally submerged under the media and completely wetted with refinement chemistry.
  • the gear was processed for six hours of refinement and a maximum of approximately 15 microns removed based on prior knowledge of the approximate material removal rate for corresponding new components.
  • the gear was periodically inspected. Inspection consisted of stopping the tub and refinement chemistry, moving the media away from a few teeth and visually assessing the progress of damage removal.
  • the refinement chemistry flow was stopped and burnish chemistry flow was immediately started using the burnish chemistry of Table VI.
  • the gear was burnished for 3 hours and deemed complete.
  • Fig. 3B is the surface roughness trace across an area of
  • the gear was processed in the refinement cycle for the stated amount of time in order to ensure all grind lines imparted during the original manufacturing were removed from the tooth flanks. Based on these observations, the part was deemed refurbished.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
  • Investigating Materials By The Use Of Optical Means Adapted For Particular Applications (AREA)
  • ing And Chemical Polishing (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Grinding And Polishing Of Tertiary Curved Surfaces And Surfaces With Complex Shapes (AREA)

Abstract

Selon l'invention, la remise en état de composants mécaniques usagés ou endommagés est effectuée à l'aide d'un procédé d'ingénierie de surface soustractif pour enlever de la matière de surfaces critiques usées ou endommagées. Le procédé met tout d'abord en jeu la réalisation du procédé sur le composant pour enlever une première quantité de matière des surfaces, l'inspection de la surface du composant pour déterminer l'étendue de la détérioration, puis la réalisation ultérieure du procédé pour enlever une quantité supplémentaire de matière si nécessaire.
PCT/US2008/010286 2007-08-28 2008-08-28 Procédé pour inspecter et remettre en état des composants mécaniques WO2009032221A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
JP2010522972A JP5714330B2 (ja) 2007-08-28 2008-08-28 工業用構成要素を検査して再製するための方法
CA2695630A CA2695630A1 (fr) 2007-08-28 2008-08-28 Procede pour inspecter et remettre en etat des composants mecaniques
DK08795724.7T DK2195139T3 (en) 2007-08-28 2008-08-28 Method for inspection and reconditioning of machine components
US12/675,712 US9180568B2 (en) 2007-08-28 2008-08-28 Method for inspecting and refurbishing engineering components
CN200880104960.5A CN101801602B (zh) 2007-08-28 2008-08-28 检查和再磨光工程部件的方法
EP08795724.7A EP2195139B1 (fr) 2007-08-28 2008-08-28 Procédé pour inspecter et remettre en état des composants mécaniques
ES08795724.7T ES2530193T3 (es) 2007-08-28 2008-08-28 Procedimiento para inspección y reconstrucción de componentes de ingeniería

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US96641707P 2007-08-28 2007-08-28
US60/966,417 2007-08-28

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WO2009032221A1 true WO2009032221A1 (fr) 2009-03-12

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US (1) US9180568B2 (fr)
EP (1) EP2195139B1 (fr)
JP (1) JP5714330B2 (fr)
KR (1) KR20100046252A (fr)
CN (1) CN101801602B (fr)
CA (1) CA2695630A1 (fr)
DK (1) DK2195139T3 (fr)
ES (1) ES2530193T3 (fr)
WO (1) WO2009032221A1 (fr)

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EP3012349A1 (fr) * 2014-10-22 2016-04-27 REM Technologies, Inc. Procédé permettant d'inspecter et de traiter des aciers d'alliage de grande dureté

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US8726778B2 (en) 2011-02-16 2014-05-20 Ervin Industries, Inc. Cost-effective high-volume method to produce metal cubes with rounded edges
US9003663B2 (en) * 2012-08-22 2015-04-14 Caterpillar Inc. Remanufacturing of bearings using isotropic finishing and thin film coatings
US9921132B2 (en) * 2014-01-03 2018-03-20 Bell Helicopter Textron Inc. Automated magnetic particle and fluorescent penetrant defect detection system
US9463548B2 (en) * 2015-03-05 2016-10-11 Hamilton Sundstrand Corporation Method and system for finishing component using abrasive media

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EP2195139A1 (fr) 2010-06-16
EP2195139B1 (fr) 2014-11-12
DK2195139T3 (en) 2015-02-16
JP5714330B2 (ja) 2015-05-07
CA2695630A1 (fr) 2009-03-12
US9180568B2 (en) 2015-11-10
CN101801602A (zh) 2010-08-11
CN101801602B (zh) 2014-07-23

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